Parachute control apparatus



y 1950 .1. R. c. QUILTER 2,505,869

PARACHUTE CONTROL APPARATUS Filed Jan. 10, 1946 2 Sheets-Sheet 1 ,[Zzwenlar wonlCdahnJ" Quiekw uus naEnT- R =& NW N? 3 3% 5 6 L h r a m A. m Wm Q. f 1 v w R ww 1 & Q Q uh 6? on \Q wm mmw I .1 3

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M y 195g J. R.-c. QUILTER 2,505,869

PARACHUTE CONTROL APPARATUS Filed Jan. 10. 1946 2 Sheets-Sheet 2 Patented May 2, 1950 05' F ICE PARACHUZTE CONTROL APPARATUS "John Raymond Cuthbert Quilter,

Woking, England;

nnlieat onil nua rtlfl, 946,.Seria 1 64 22 lnfircatfiritain February 15,1945- This invention relates to parachute apparatus and-more particularly in automatic apparatus for controlling the deployment of parachutesfor occupants of aircraft livin at great'height where the-lack of oxygen is liable torende them un conscious uponleaving or'being ejectedfrom the aircraft. In such conditions, it is desirable to allow the pilot or other occupant to fall freely until he reaches alevel at which the atmosphere is" more favourable to hisrecovery and'torelease the parachute only atthif rfidetermined height; for'example, in the ease of a jet-p Q elled aircraft flying at -50;000feet, if :the pilot'were to leaveor be ejected from the aircraft, the automatic control would b e started or set ready for operation, but would delay bringing the parachute into action until the pilot ,had fallen freely to the denser atmosphere at a height of say 101100 feet.

The inventionhasfor-its main objectito provide improvedapparatus ofthis character; suitable for releasing the parachute by withdrawing the customary ripcord pin of 'thC pHCk .wornby a pilot or other occupant.

Another .object of the invention is to provide .a servomotorforefiectingthe release;;the operation of the servomotor. being controllediby abarometric device of small size .which canbe readily accom modated upon the harness or upon the parachute pack.

A further object istoprpvide improvedappa'ratus of this character, wherein thenormalmanua l release is adapted to overrid the automatic controlif so desired, inorder thatzthfi same parachuteequipment maybe available for use atlower altitudes when the manual release can be employed without regard to the automatic control.

Other objects and advantages of'the invention will hereinafter appear from the following description of two suitable embodiments, given with 1 reference to the accompanying drawings, in

- which:

Fig. is a'detail in section cn the li-neL-fi .of

Fig. 1'.

Fig. 5 is a sectionalview of a pyrotechnic servomotor for the withdrawal of the rip-cord pin from the pack.

Fig. '6 shows the'location of thebarometric deill 2 viceand servomotor upon the parachute harness, to ether with the rip-cord handle for manual op:- eration of the release.

Fig. 7=isa diagram ofth'e electrical connections.

Fig. 8 illustratesan alternative form of servomotor comprising a clockwork adapted to tripe. spring for-the release of the pack, the barometric device being enclosed in the samecasing as the clockwork.

Referring to Figs. lto i, tlie barometric device comprises a beil -shaped casing H closedbyan end cover 12 and enclosing a seriesof aneroid capsules l3 fixed at one end upon-apost Mwhich extends'through the cover 42 the movable endlof the capsules it carries ascrewrthreadeol rodl5 passingfreely through a hole in the casing and through-a metal bar it secured diametrically across the exterior of the casing by means of screws [1. The rod 45 is fitted with an adjustablecollar l8' having a serrated edge adapted to make contact withthe bar ifipbut the expansion of the capsules due to the reduction of atmospheric pressure above a predetermined height moves the-collar 18 clear of the bar 16, contact.

beingre-established upon return of the predetermined height, as during the descentoi a pilot escaping-froman'aircraft,

The casing I I of the barometric device is shown secured upon a-metal base plate l9, one end of which is bent up at rightanglestoform a wall 29, between which and the Casing ll there is fittedia block 2-! of-insulatingmaterial such as ebonite. Another block 22,a1s0 of insulating material, is secured to theother end' of the base plate, this block being'recessed at 23 to allow freedom "of movement of the rod I5. Two side rails 24, of angle section, are fixed to blocks 2| and 22 by screws 25, theoutwardflanges of these side rails being-perforated at 25 to enable the device tobe fixed upon any convenient part of the harness or paclg for examplebystitching'. The uppertedges of the blocksZ! and22 are rounded to semi-circular form, as seen in 'Fig. 2; a curved shield 2! beingfitted over them andsecured" in place by screws 28; the bottom edges of the shield 21' are substantially flush with the upper edges of the side rails '24.

The-block?! isof stepped formation, providing awall portoniilibeside the wall 2fl-ofthe base plate; a recess 30, a lower siielf 3! andan upper shelf 32-. Againsttheinneriace 'of the wall portion 29;there is fitteda contact plat 2-3, secured bya screw 34 extendingthrough the wallEll-of the base--plate.. Atthe bottom "of therecess '50 there are provided fourtermina-is 35, to which are connected the two pairs of leads 36 from twotwin-wire detonator cables 31 passing through holes in the wall 20. Upon the lower shelf 3!, there is detachably mounted a two-cell electric battery 38, secured by means of a central stud 39 fixed in the shelf, with a nut 43 and Washer upon the upper end of the stud; both poles of the two cells at one end of the battery engage with the contact plate 33. Upon the upper shelf 32, there are mounted two separate overhanging contact strips 4| which engage with the other poles of the two cells; these strips are secured by screws 42, from which leads 43 extend to the two outer terminals 35.

The two inner terminals 35 are connected together by a common lead 44 extending along a.

46 upon the post l4; the latter connects electricala ly-through the capsule assembly with the rod- I and collar ill at the other end.

The single contact plate 33 is connected by its screw 34, and by a lead 4! extending along grooves in the block 2!, to one pole of a plunger switch 48 enclosed in the lower part of the block, the other pole of this switch being connected by a lead 49 to one of the screws H of the bar I6; as shown in Fig. 4, the switch 48 comprises a plunger rod 50 slidable in a guide tube 5! of in sulating material, which is screwed into a transverse hole in the block, the rod carrying a contact disc or cone 52 adapted to bridge two insulated contact segments 53 near the head of the'tube 5|. A plug 54 screwed into the other end of the tube provides an abutment for a spring 55 coiled around the rod 50, the latter projecting through the plug 54 and having its outer end formed into an eye 55; this eye can be engaged by a locking pin 5'! guided in holes 58 in the block, such engagement retaining the plunger switch in open position. The locking pin 51 will be withdrawn by the pull of a static line attached to some convenient part of the aircraft, for ex-- ample to the pilots seat, so that until he leaves his seat, the plunger switch will remain open and the electrical circuit controlled by the barometric device cannot be closed.

When, however, the locking pin 51 has been withdrawn and the switch 45 has therefore closed by operation of the spring 55, the circuit will be prepared for completion as soon as the capsules I3 are collapsed to the required extent by the increasing atmospheric pressure as the pilot descends; at the predetermined altitude, for example at 10,000 feet, the capsules will bring the collar I 8 into contact with the bar I6, thereby completing the circuit of the detonator cables 31. These cables extend to a pyrotechnic servo motor illustrated in Fig. 5, where they are connected to two firing bridges I58 for igniting the gun-powder charges or initiators of an explosive cartridge 59, adapted to operate the rip-cord release of the parachute pack. The cartridge comprises a suitable propellant charge 6E! enclosed in the base of a shell BI provided with flanges 52 perforated for stitching to any convenient part of theharness or pack; the firing bridges I58 are secured an annular lid 63 closing the end of the shell and supporting a coaxial tube or cylinder 64. Around this cylinder, between the propellant charge Iii! and the gunpowder charge 65 in which the firing bridges are embedded, there is packed a delay ,composition 66, giving a period of two seconds -for examplebetween thefiring or -the parachute is released. The other end of the ripcord extends from the piston 68, outwardly of the cylinder 64, and is attached to a handle 12 by which the rip-cord pins can be operated manumounted by means of its perforated side rails 24 upon one side of the harness belt 13, at a suitable distance from the parachute pack 14, and the pyrotechnic servomotor is similarly mounted by means of its perforated flanges 62; the rip-cord pins H are engaged in the locking studs which maintain the pack in closed condition. The ripcord extends laterally from the pack by way of a guide casing I6, through the servomotor l1, and by way of-a second length of guide casing 15, its other end being attached to the handle 12 supported. upon the belt 73 or other convenient part of the harness; thus the normal manual release can override the automatic control if the pilot so desires. The same parachute equipment will therefore be available for use at lower heights than the predetermined altitude at which the automatic control is adjusted to operate, and the manual release handle can be employed at any time .without' regard to the automatic control v Fig. '7 shows the electrical connections of the barometric device and pyrotechnic servomotor. The circuit may be traced from the positive poles of the battery 38,, in contact with the plate 33, by way of screw 34, lead 41, to the plunger switch 48, and from the latter by way of lead 49 to the bar I5; the collar I8, adapted to contact with the bar, is connected by the screwed rod I5, capsules I3, ost 14, lead 44, and the two central terminals to one conductor of each detonator cable 31, through the firing bridges I58, back through the other conductor of the cables 3'! to the outer terminals 35, and from the latter by leads 43 to the strips 4| in contact with the negative poles of the respective cells of battery 38.

Any suitable form of barometric device adapted for operation by atmospheric pressure may be employed to withdraw the rip-cord pin automati cally by the aid of the servomotor.

Otheriorms of servomotor may be employed instead of the pyrotechnic device described above; for example, Fig. 8 represents a clockwork mechanism, adapted to release a spring in order to open the pack. In this example, the barometric device comprises aseries 0f aneroid capsules I8, fixed at one end to the wall of the casing I9, the'other end of the capsule series carryinga friction pad 8!! in breaking contact with the bal; ance wheel 8! of-the clockwork B2 which-is driven by a spring barrel 83 one of the clockwork spindles carries a pinion 84 meshing with-a toothed rack of which one extremity forms a latch 83 siidable in and out ofthe casing I9. When projecting, this latch engages an arm 8'1, pivoted at 88, against which a powerful coiled spring 89 presses; movement of the arm by the spring is normally prevented by the latch. The rip-cord 9Q extendsaxiallythrough the spring 89 and passes through a hole in the arm, adjacent to which it is fitted with a collar 9! this end of the rip-cord is connected to a handle 92 for manual operation, the pull being unaffected by the latching of the arm 81. The other end of the rip-cord extends to the pack, where it carries the pins 93 normally locking the closure flaps, as already described.

Operation of the barometric device may be prevented, during the normal climb of the aircraft until the predetermined altitude has been reached. by a locking pin 96 which maintains a second friction pad 95 in contact with the balance wheel; this locking pin will be withdrawn by a static line 95 or other attachment to the aircraft, when the pilot makes his escape, or alternatively the pin 94 can be withdrawn manually by means of a lever or handle 97 having a forked end 98 which engages the pin 94, without obstructing the direct pull of the static line 98. will then be lifted from the wheel Bl by a spring 99 and the other pad 89 will also be lifted by the collapse of the aneroid capsules at the predetermined height, after which the latch 85 is freed at the end of a short period of say two seconds by the operation of the clockwork, so that the pack will be opened automatically by the stressed spring 89. The handle 92 provides an overriding action which can effect the release at any time desired by the pilot.

What I claim is:

1. Parachute control apparatus, comprising a parachute pack, means for retaining said pack in closed condition, a rip cord having a handle for withdrawing said retaining means to cause release of the parachute, a piston secured to said rip cord, a cylinder for said piston, a propellant charge adapted to produce explosion gases for driving said piston along said cylinder in a direction to cause withdrawal of said retaining means by said rip cord, a barometric device responsive to altitude, means for igniting said propellant charge by the response of said barometric device at descent to a predetermined altitude, means normally rendering said barometric device inoperative to ignite said propellant charge, and automatic means for rendering said barometric device operative upon descent from an aircraft, said rip cord being manually operable by means of its handle for withdrawing said retaining means independently of said piston.

2. Parachute control apparatus, comprising a parachute pack, means for retaining said pack in closed condition, a rip cord for withdrawing said retaining means to cause release of the parachute, a piston secured to said rip cord, a cylinder for said piston, a propellant charge adapted to produce explosion gases for driving said piston along said cylinder in a direction to cause withdrawal of said retaining means by said rip cord, a barometric device responsive to altitude, means for igniting said propellant charge by the response of said barometric device at descent to a predetermined altitude, means normally rendering said barometric device inoperai'he pad 95 tive to ignite said propellant charge, means for rendering said barometric device operative upon descent from an aircraft, and manual means for operating said rip cord to cause withdrawal of said retaining means, said manual means being adapted to override the control exerted by said barometric device.

3. Parachute control apparatus, comprising a parachute pack, means for retaining said pack in closed condition, a rip cord having a handle for withdrawing said retaining means to cause release of the parachute, a collar fixed upon said rip cord, a pivoted arm mounted adjacent to said collar, a spring pressing said arm against said collar in a direction to withdraw said retaining means, a latch normally engaging said arm to hold it fast against the pressure exerted by said spring, a timing mechanism adapted to release said latch, two separate means normally preventing the start of said timing mechanism, automatic means for freeing one of said separate preventing means at initial descent from an aircraft, and a barometric device responsive to altitude for freeing the other of said separate preventing means at descent to a predetermined altitude, said rip cord being manually operable by means of its handle for withdrawing said retaining means independently of the release of said latch.

4. Parachute control apparatus, comprising a parachute pack, means for retaining said pack in closed condition, a harness belt carrying said pack, a rip cord for withdrawing said retaining means to cause release of said parachute, a handle for operating said rip cord, said handle mounted on said belt, a servomotor mounted on said belt and adapted to operate said rip cord, a barometric device responsive to altitude and adapted to cause operation of said servomotor at descent to a predetermined altitude, said barometric device mounted on said belt, means normally rendering said barometric device inoperative to operate said servomotor, and a static line attachable to an aircraft for rendering said barometric device operative upon descent from said aircraft, the operation of said rip cord by said handle overriding the control exerted by said barometric device when inoperative.

JOHN RAYMOND CUTHBERT QUILITER.

REFERENCES CITED The following references are of record in the file of this patent:

UNITED STATES PATENTS Number Name Date 1,535,475 Jeansen et a1 Apr. 28, 1925 1,800,575 Toffiemire Apr. 14, 1931 1,944,795 Lafayette Jan. 23, 1934 2,110,552 Hayden Mar. 8, 1938 2,365,445 Badowski Dec. 19, 1944 FOREIGN PATENTS Number Country Date 278,695 Great Britain Apr. 5, 1928 

